Wing float drag



June 18, 1946. 5 G 2,402,379

WING FLOAT DRAG Filed Oct. 19, 1943 2 Sheets-Sheet l Wgj ATTORNEYS.

June 18, 1946. c, DE GANAHL WING FLOAT DRAG 2 Sheets-Sheet 2 Filed Oct.19, 1943 INVEN TOR. (:z/'/ 64am 6/ A TTORNE Y3.

Patented June 18 1946 PATE NT *oFFIcEfY- WING FLOAT DRAG Carl de Ganahl,Trenton, N. J assignor to Kaiser Cargo, Inc., Bristol, P

fornia a., a corporation of Cali- Appl ication October 19, 1943, SerialNo. 506,832

4 Claims.

Thi is due to the fact that on a, plane of this type the stabilizer andair rudder have large areas. When wind velocities of 1520 miles an houror more are attained, more pressureis ex- 7 erted on these surfaces thanthe water rudder alone can counteract, Consequently the operator cannotsuccessfully control movement of the plane on the water. 7

It is the object of the invention to provide a simple and effectivemeans which is readily controllable by the operator to ensure themovement of the plane in the desired course upon the water. Anotherobject of the invention is the provision of devices, subject preferablyto remote control, whereby suitable drag may be applied to the wingfloats as required to resist the tendency due to wind pressure on thefln and air rudder of the plane to move into the wind.

Other objects and advantages of the invention will be apparent as it isbetter understood by reference to the following specification andaccompanying drawings, in which Fig. 1 is a side elevation of a wingfloat embodying one form of the invention;

Fig. 2 is a cross-section on the line 2--2 of Fig. 1;

Fig. 3 is an elevation illustrating a slightly modified form of theinvention; Fig. 4 is an elevation illustrating another modification; I aFig. 5 is an elevation illustrating another modification;

Fig. 6 is a rear end elevation of the wing float as shown in Fig. 5; and

Fig. 7 is a sectional View of a modification of the drag device similarto that shown in Fig. 5.

In carrying out the invention, I provide adjustable members connected tothe wing floats of the plane below the water line and capable ofcontrolled movement to and from positions in which the members may beinefiective or may introduce drag by resistance to the water in whichthe floats rest. Such members may have various forms and they may besupported in different ways. They may be actuated by suitable motors ofthe hydraulic or other type. Preferably double acting hydraulic motorsor jacks are used with suitable arrangements well known in the artwhereby the motors may be controlled from a central point such as thepilots seat. In one desirable form, the adjustable members are flapspivoted in recesses in the bottoms ofthe floats and having the generalcontour thereof, sothat they offer no added resistance when in closedposition. 'The flaps may be adjacent the stems of the floats oramidships thereof, and may be pivoted to swing outwardly incounter-clockwise or clockwise directions as desired.

In another form, the adjustable members may be shaped to conform to thelower section of the stems of the floats and may be projected thereandconstruction. As indicated in Fig. 1 a flap 1 is pivoted at 8 near thestern of the wing float 5 and normally is disposed in a recess 9 in thebottom of the wing float. The flap 1 has a surface conforming to thebottom of the wing float 5 and normally oifers no resistance to themovement of the wing float through the water. To alford the desireddrag, the flap 1 is projected to the position indicated in dotted lines.

Movement is effected by means of a hydraulic jack I0 which is supportedfor pivotal movement on trunnions ll within the wing float 5. A bellowsll' permits pivotal movement of the jack and prevents water fromentering the float. A ram 12 is connected by a rod l3 to the flap l. Therod 13 passes through a suitable stufflngbox M. The ram 12 may be causedto move in either direction .by hydraulic pressure introduced throughpipes l5 and [6 which are connected to the usual hydraulic system of theplane and provided with the customary controls whereby the pilot mayactuate the jack l0 and thus project or withdraw the flap 1. As alreadyindicated, the floats on opposite sides of the plane may be providedwith flaps 7 which are independently operable by the pilot. When eitheror both of the flaps l are in the outward position, the flaps willafford additional resistance and thereby facilitate control of the planewhen it is subjected to wind pressures which otherwise would causeerratio operation.

The structure as illustrated in Fig. 3 is substantially identical withthat shown in Fig. 1, with the exception that the flap 1' is pivoted at8' inboard of the stern. A jack having a ram I2 actuates the flap 1'through a rod l3. Pipes l5 and I6 permit the introduction of fluid underpressure to effect operation of the ram 12' in opposite directions andthus to open and close the flap 1.

In the structure as illustrated in Fig. 4, the flap 1" is pivoted at 8".In this case, the flap is disposed approximately amidships of the float5. It may be pivoted at either end, but is preferably arranged with thepivot toward the stern of the float. A jack I0" is provided with a raml2" and. the latter is connected by a rod 13" to the flap 1'. Pipeconnections l5" and i6" permit the application of fluid to the jack toeffect operation of the flap 1" in the manner and for the purposehereinbefore described.

In Fig. 5, the drag device takes a different form, being substantially asection of the stern of the float. Thus the stern of the float may becut away on the line ab and a member I! is shaped to conform with thecut-away section. This member is connected by a ball joint 18 to a rodI9 extending through a stuiflng box 20 into a jack 2|. The rod isconnected to a ram 22. The jack is pivoted on a trunnion 23 so that itmay swing about the pivot to adjust itself to different positions of themember l1. Pipes 24 and 25 permit the introduction of fluid underpressure to the jack at either end so that the member H may be projectedand may assume various positions as indicated in dotted lines in thefigure. Thus the operator can project the member I! or withdraw it. Whenprojected, it will afford the necessary drag, and when withdrawn it willbe ineffective. As in the case of other forms of the invention, thefloats 5 on Opposite sides of the plane will each be provided withmembers I! independently operable to attain the desired result.

Instead of cutting away the rearward part of the float 5 as indicated inFig. 5, the surface may be rabbeted and the member l1 may be formed tofit over the rabbeted surface when it is in normal position, as shown inFig. 7. When projected, it will form a hollow, cup-like member affordingeven greater resistance to the water than the form of the device shownin Fig. 5. The member II will be connected by a ball joint to a rod l9and thus to a ram 22' within a jack 2|. Actuation will be effected bythe introduction of fluid pressure through the pipes 24 and 25' as inthe preceding embodiments of the invention.

Although hydraulic jacks are simple devices which are well known in theart and are easily controllable and therefore suitable for the purpose,other forms of motors may be employed. Any type of reversible motorwhich will permit projection and withdrawal of the flaps or equivalentdrag devices may be employed, the essential of the invention being theprovision of drag devices below the water line of the floats whichnormally aflord no resistance to the movement of the floats and aremovable to introduce drag under control of the pilot to counteract windpressure on the fin and air rudder of the plane.

Various changes may be made in the details of arrangement andconstruction of the parts without departing from the invention orsacrificing the advantages thereof.

I claim:

1. In an airplane wing float, a member shaped to conform to the lowerstern edge of the float, said member normally lying against the lowerstern edge of the float and offering no substantial resistance to themovement of the float through water, means carried by and within saidfloat and attached to said member to project said member outwardly intothe water to produce drag, and means associated with said projectingmeans to prevent leakage of water into the float.

2. In an airplan wing float having an inclined planar surface along itslower stern edge, a member of triangular cross section adapted to lieagainst said inclined surface and to complete the lower stern edge ofthe float, said member normally offering no resistance to the movementof the float through water, means carried by said inclined surfacewithin said float and attached to said member to project said memberoutwardly into the water to produce drag, and means associated with saidprojecting means to prevent leakage of water into the float.

3. In an airplane wing float, a member shaped to conform to the lowerstern edge of the float, said member normally lying against the lowerstern edge of the float and offering no substantial resistance to themovement of the float through water, hydraulic means carried by andwithin said float and attached to said member to project said memberoutwardly into the water to produce drag, and means associated with saidprojecting means to prevent leakage of water into the float.

4. In an airplane wing float, a member shaped to conform to the lowerstern edge of the float, said member normally lying against the lowerstern edge of the float and offering no substantial resistance to themovement of the float through water, hydraulic means within said floatand attached to said member to project said member outwardly into thewater to produce drag, pivotal means affixed to the float, saidhydraulic means being pivotally carried by said pivotal means to permitadjustment thereof according to the drag position assumed by saidmember, and means associated with said projecting means to preventleakage of water into the float.

CARL DE GANAHL.

